Electronic module mounting to vibration isolating structure

ABSTRACT

An electromechanical component arrangement for a gas turbine engine includes a mechanical component located at a first side of a firewall of a gas turbine engine and an electronic module of the electromechanical component in communication with the mechanical component separated from the mechanical component by a firewall, the firewall comprising a first side and a second side, the second side having a lower operating temperature than the first side. A vibration isolation structure is located at the second side. The electronic module is connected thereto and includes at least one vibration isolator secured to the firewall to vibrationally isolate the electronic module from gas turbine engine vibrations.

BACKGROUND

This disclosure relates to gas turbine engines, and more particularly tothe thermal protection of electrical components of gas turbine engines.

Electrical components are by their nature sensitive to temperature andthermal cycling. As a result, it is desired to keep the electricalcomponents relatively cool and within a small temperature range in orderto function properly and to extend the useful service life of theelectrical components. Many mechanical system components such a pumps,actuators, valves, or the like are driven by electrical motors, andwhile the mechanical portion of the component may be able to withstandhigh operating temperatures, the electrical portions of the components,such as a motor, controller and other portions, must be kept relativelycool to maintain their useful service life. In a typical gas turbineengine, a “firewall” is defined that divides a “cold side” of the gasturbine engine where temperatures are typically below 160 degreesFahrenheit from a “hot side” of the gas turbine engine where operatingtemperatures are often in the range of about 160 degrees to 600 degreesFahrenheit or higher. Problems arise when it is desired or necessary tolocate a mechanical component with necessary electrical portions such asa motor or a controller on the “hot side” of the firewall.

SUMMARY

In one embodiment, an electromechanical component arrangement for a gasturbine engine includes a mechanical component located at a first sideof a firewall of a gas turbine engine and an electronic module of theelectromechanical component in communication with the mechanicalcomponent separated from the mechanical component by a firewall, thefirewall comprising a first side and a second side, the second sidehaving a lower operating temperature than the first side. A vibrationisolation structure is located at the second side. The electronic moduleis connected thereto and includes at least one vibration isolatorsecured to the firewall to vibrationally isolate the electronic modulefrom gas turbine engine vibrations.

Additionally or alternatively, in this or other embodiments a coverplate is installed over the module opening after the electronic moduleis inserted therethrough.

Additionally or alternatively, in this or other embodiments theelectronic module is operably connected to one or more of an electricalcontroller or an electrical motor located at the second side of thefirewall.

Additionally or alternatively, in this or other embodiments thevibration isolation structure further includes a connection hub tooperably connect the electronic module to the one or more of theelectrical controller or the electrical motor.

Additionally or alternatively, in this or other embodiments thevibration isolator is one or more of a spring, an elastomeric damper, anair cylinder/piston arrangement or an oil filled cylinder/pistonarrangement.

Additionally or alternatively, in this or other embodiments theelectronic module is configured to collect and indefinitely store datafrom the mechanical component relating to the service life and/oroperation of the mechanical component.

Additionally or alternatively, in this or other embodiments anelectrical motor is located at the second side of the firewall andoperably connected to the mechanical component via a coupling extendingthrough the firewall at a coupling opening, separate and distinct fromthe module opening.

Additionally or alternatively, in this or other embodiments anelectrical controller is located at the second side and operablyconnected to the electronic module and the electrical motor to controlthe electrical motor utilizing input from the electronic module.

Additionally or alternatively, in this or other embodiments theelectronic module is inseparably affixed to the mechanical component toremain connected to the mechanical component for the entire service lifeof the mechanical component.

Additionally or alternatively, in this or other embodiments the firstside has an operating temperature greater than 160 degrees Fahrenheit.

Additionally or alternatively, in this or other embodiments the firewallis disposed axially upstream of a high pressure compressor section ofthe gas turbine engine, the first side located axially downstream of thefirewall.

In another embodiment, an electromechanical system for a gas turbineengine includes a mechanical component located at a first side of afirewall of a gas turbine engine, an electrical motor located at asecond side of the firewall, the second side having a lower operatingtemperature than the first side. The electrical motor is operablyconnected to the mechanical component via a coupling extending through acoupling opening in the firewall and configured to drive the mechanicalcomponent. An electronic module is connected to the mechanical componentby a module cable. The electronic module is inserted through a moduleopening in the firewall from the first side to a second side. Avibration isolation structure is located at the second side. Theelectronic module is connected thereto and includes at least onevibration isolator secured to the firewall to vibrationally isolate theelectronic module from gas turbine engine vibrations. A cover plate isinstalled over the module opening after the electronic module isinserted therethrough.

Additionally or alternatively, in this or other embodiments theelectronic module is operably connected to an electrical controllerdisposed at the second side of the firewall. The electrical controlleris configured to control the electrical motor utilizing input from theelectronic module.

Additionally or alternatively, in this or other embodiments thevibration isolation structure further includes a connection hub tooperably connect the electronic module to the electrical controller.

Additionally or alternatively, in this or other embodiments thevibration isolator is one or more of a spring, an elastomeric damper, anair cylinder/piston arrangement or an oil filled cylinder/pistonarrangement.

Additionally or alternatively, in this or other embodiments theelectronic module is configured to collect data from the mechanicalcomponent relating to the service life and/or operation of themechanical component.

Additionally or alternatively, in this or other embodiments the data isone or more of operating speeds, temperatures, pressures, flow oroperational time of the mechanical component.

Additionally or alternatively, in this or other embodiments themechanical component is one of an actuator or a pump.

Additionally or alternatively, in this or other embodiments the firstside has an operating temperature greater than 160 degrees Fahrenheit.

In yet another embodiment, a gas turbine engine includes a high pressurecompressor, a combustor in operable communication with the high pressurecompressor and a firewall located axially upstream of the high pressurecompressor. The firewall defines a first side axially downstream of thefirewall and a second side axially upstream of the firewall, the secondside having a lower operating temperature than the first side. Anelectromechanical system includes a mechanical component located at thefirst side and an electrical motor located at the second side. Theelectrical motor is operably connected to the mechanical component via acoupling extending through a coupling opening in the firewall andconfigured to drive the mechanical component. An electronic module isconnected to the mechanical component, the electronic module insertedthrough a module opening in the firewall from the first side to a secondside. A vibration isolation structure is located at the second side. Theelectronic module is connected thereto and includes at least onevibration isolator secured to the firewall to vibrationally isolate theelectronic module from gas turbine engine vibrations. A cover plate isinstalled over the module opening after the electronic module isinserted therethrough.

BRIEF DESCRIPTION OF THE DRAWINGS

The subject matter which is regarded as the present disclosure isparticularly pointed out and distinctly claimed in the claims at theconclusion of the specification. The foregoing and other features, andadvantages of the present disclosure are apparent from the followingdetailed description taken in conjunction with the accompanying drawingsin which:

FIG. 1 illustrates a schematic cross-sectional view of an embodiment ofa gas turbine engine;

FIG. 2 illustrates a schematic view of an embodiment of a componentarrangement at a firewall of a gas turbine engine;

FIG. 3 illustrates a schematic perspective view of an embodiment of acomponent connection arrangement at a firewall of a gas turbine engine;

FIG. 4 illustrates a schematic view of another embodiment of a componentconnection arrangement at a firewall of a gas turbine engine; and

FIG. 5 illustrates another schematic view of the embodiment of FIG. 4.

DETAILED DESCRIPTION

FIG. 1 is a schematic illustration of a gas turbine engine 10. The gasturbine engine generally has includes fan section 12, a low pressurecompressor 14, a high pressure compressor 16, a combustor 18, a highpressure turbine 20 and a low pressure turbine 22. The gas turbineengine 10 is circumferentially disposed about an engine centerline X.During operation, air is pulled into the gas turbine engine 10 by thefan section 12, pressurized by the compressors 14, 16, mixed with fueland burned in the combustor 18. Hot combustion gases generated withinthe combustor 18 flow through high and low pressure turbines 20, 22,which extract energy from the hot combustion gases.

In a two-spool configuration, the high pressure turbine 20 utilizes theextracted energy from the hot combustion gases to power the highpressure compressor 16 through a high speed shaft 24, and the lowpressure turbine 22 utilizes the energy extracted from the hotcombustion gases to power the low pressure compressor 14 and the fansection 12 through a low speed shaft 26. The present disclosure,however, is not limited to the two-spool configuration described and maybe utilized with other configurations, such as single-spool orthree-spool configurations.

Gas turbine engine 10 is in the form of a high bypass ratio turbineengine mounted within a nacelle or fan casing 28 which surrounds anengine casing 30 housing a engine core 32. A significant amount of airpressurized by the fan section 12 bypasses the engine core 32 for thegeneration of propulsive thrust. The airflow entering the fan section 12may bypass the engine core 32 via a fan bypass passage 34 extendingbetween the fan casing 28 and the engine casing 30 for receiving andcommunicating a discharge flow F1. The high bypass flow arrangementprovides a significant amount of thrust for powering an aircraft.

The engine casing 30 generally includes an inlet case 36, a low pressurecompressor case 38, and an intermediate case 40. The inlet case 36guides air to the low pressure compressor case 38, and via a splitter 42also directs air through the fan bypass passage 34.

The gas turbine engine 10 further includes a firewall 44, defined toseparate a relatively high temperature portion of the gas turbine engine10, where operating temperatures may be in the range of 160 degrees to600 degrees Fahrenheit or higher, from a relatively low temperatureportion of the gas turbine engine 10, where operating temperatures areless than about 160 degrees Fahrenheit. In the embodiment of FIG. 1, thefirewall 44 is located between the low pressure compressor 14 and thehigh pressure compressor 16, separating a cold side 46 of the gasturbine engine 10 where operating temperatures are less than about 160degrees Fahrenheit, from a hot side 48 of the gas turbine engine 10,where operating temperatures may be in the range of 200 degrees to 600degrees Fahrenheit or higher. The hot side 48 includes engine areas andcomponents axially downstream of the firewall 44, while the cold side 46includes engine areas and components axially upstream of the firewall44.

Referring now to FIG. 2, the gas turbine engine 10 includes manymechanical components 50 or devices such as actuators, pumps or thelike, and many of these mechanical components 50 utilize electricalcomponents, such as electrical motors 52 and/or electrical controllers54 to enable or control operation of the mechanical components 50. It isoften desired or necessary to locate such mechanical components 50 atthe hot side 48 of the firewall 44, but care must be taken to protectthe electrical components from the high operating temperatures of thehot side 48.

Shown in FIG. 2 is an embodiment of an arrangement in which themechanical component 50, such as an actuator or pump, is located at thehot side 48 of the firewall 44. A coupling 56, such as a shaft extendsfrom the mechanical component 50 through a coupling opening 58 in thefirewall 44 and connects to the electrical motor 52, located at the coldside 46 of the firewall 44. A coupling seal 60 may be located at thecoupling opening 58 to seal between the coupling opening 58 and thecoupling 56 to prevent migration of hot gases from the hot side 48 tothe cold side 46 through the coupling opening 58. The mechanicalcomponent 50 includes an electronic module 62 at which collects datarelating to the service life and operation of the mechanical component50 is stored. The data may include recorded operating speeds,temperatures, pressures, flow, operational times or the like and mayinclude data measured by one or more sensors 64 at the mechanicalcomponent 50. The electronic module 62 is inseparably secured to themechanical component 50 to remain with the mechanical component 50through the lifespan of the mechanical component 50. Data collected atthe electronic module 62 will remain with the mechanical component 50even when the mechanical component 50 is removed from the gas turbineengine 10 for service, repair or replacement.

The electronic module 62 receives power from the electrical controller54 and converts analog signals from cable 66 into digital signals fortransmission to the electrical controller 54 through a controller cable72. The electronic module 62 may include any combination of a powerconditioning function, processing unit, memory, analog to digitalconverters, analog interface circuits and a digital bus interface forcommunication. Other circuits that interface devices in the mechanicalcomponent 50 may also be included in the electronic module 62.

To protect the electronic module 62 from the high operating temperaturesof the hot side 48 and to preserve the integrity of the data collectedat the electronic module 62, the electronic module 62 is located at thecold side 46 of the gas turbine engine 10. To accomplish this, theelectronic module 62 is connected to the mechanical component 50 via amodule cable 66, which permanently joins the electronic module 62 to themechanical component 50. With the mechanical component 50 installed atthe hot side 48, the electronic module 62 is passed through a moduleopening 68 in the firewall 44 from the hot side 48 to the cold side 46.A cover plate 70, which may be installed around the module cable 66 orintegral to the module cable 66 covers and seals the module opening 68from the hot side 48 to prevent hot gas egress from the hot side 48 tothe cold side 46 via the module opening 68. Once in place at the coldside 46, the electronic module 62 is connected to one or more componentson the cold side 46 such as the electrical controller 54 via thecontroller cable 72 to provide communication between the mechanicalcomponent 50 and the electrical controller 54 so the electricalcontroller 54 may provide commands to the electrical motor 52 via motorcable 74 to, for example, adjust output of the electrical motor 52 basedon data feedback from the mechanical component 50 and/or the electronicmodule 62. While the controller cable 72 and motor cable 74 areillustrated in FIG. 2, it is to be appreciated that in otherembodiments, the controller cable 72 may be omitted and the electronicmodule 62 may be directly connected to the electrical controller 54.Likewise, in some embodiments the electrical motor 52 may be directlyconnected to the electrical controller 54, with the motor cable 74omitted. Also, while the electronic module 62 in the embodiment of FIG.2 is connected to the electrical controller 54, it is to be appreciatedthat in other embodiments, the electronic module 62 may be connected tothe electrical motor 52 or another electrical or mechanical component.Further, the electronic module 62 may be fixed in place to, for example,the cover plate 70, the firewall 44 or other structure of the gasturbine engine 10. In some embodiments, the electronic module 62 mayalso be in communication with the mechanical component 50 wirelessly.

Referring now to FIG. 3, in some embodiments it is desired to protect orisolate the electronic module 62 from high frequency vibrations thatoccur during operation of the gas turbine engine 10, which may betransmitted through the firewall 44 or cover plate 70. FIG. 3illustrates a vibration isolation structure 76 to which the electronicmodule 62 is secured, and connected to the controller cable 72. Thevibration isolation structure 76 includes a connection hub 78 at whichthe electronic module 62 is connected to, for example, the controllercable 72. The connection hub 78 is spaced from and connected to thefirewall 44, or other structure of the gas turbine engine 10, by one ormore vibration isolators 80, such as springs, dampers such aselastomeric dampers, and/or other vibration absorbing or damping elementsuch as an air cylinder/piston arrangement or an oil filledcylinder/piston arrangement. While two vibration isolators 80 are shownin FIG. 3, it is to be appreciated that other quantities of vibrationisolators 80, for example, one, three, four or more vibration isolators80 may be utilized. The vibration isolators 80 are configured such thattransmission of gas turbine engine 10 high frequency vibrations from thefirewall 44 to the electronic module 62 is reduced or prevented.

To further prevent vibration transmission to the electronic module 62,the module cable 66 extending from the cover plate 70 to the electronicmodule 62 is in a slack condition (not taut) after the electronic module62 is installed at the connection hub 78 and the cover plate 70 isinstalled to the firewall 44. Cable springs 82 may extend from the coverplate to the electronic module 62 to further dampen vibration which maybe transmitted through the module cable 68.

Another embodiment of a vibration isolation structure 76 is shown inFIGS. 4 and 5. The vibration isolation structure 76 includes a housing84 fixed to the cover plate 70 with, in some embodiments, a seal 86interposed between the housing 84 and the cover plate 70. A mountingframe 88 is located in the housing 84 with the electronic module 62secured to a first leg 90 of the mounting frame 88. The mounting frame88 includes a leg 92, which in some embodiments is perpendicular to thefirst leg 90. In some embodiments, the mounting frame 88 issubstantially T-shaped. The mounting frame 88 is supported in thehousing 84 by one or more vibration isolators 80 connected to thehousing 84 and to the mounting frame 88. The vibration isolators 80support the mounting frame 88 in the housing 84 while allowing forrelative vibratory motion of the mounting frame 88 and electronic module62 relative to the housing 84 and the cover plate 70. Gas turbine engine10 vibrations transmitted through the firewall 44 and cover plate 70into the housing 84 are dampened by the vibration isolators 80 sotransmission to the electronic module 62 is reduced or prevented. Toallow for the relative vibratory motion of the cover plate 70 relativeto the electronic module 62, the module cable 66 may have a slack (nottaut) condition when the cover plate 70 is installed to the firewall 44to prevent vibration transmission through the module cable 66 to theelectronic module 62.

To connect the electronic module 62 to the controller cable 72 or othercomponent, the connection hub 78 is located at the housing 84, providinga connector 94 for connecting the controller cable 72. The electronicmodule 62 is connected to the connector 94 of the connection hub 78 viaan intermediate cable 96, which also may have a slack (not taut)condition to allow for relative vibratory motion between the housing 84and the electronic module 62, thus preventing vibration transmissionthrough the intermediate cable 96 to the electronic module 62.

The embodiment of FIGS. 4 and 5, including the housing 84 with theelectronic module 62 located inside of the housing 84, providesadditional protection of the electronic module 62 from damage orcontamination, both when installed at the gas turbine engine 10 and whennot installed at the gas turbine engine 10. Further, the housing 84provides a rigid structure to ensure that when the housing 84 isinstalled through the firewall 44, a secure connection is made with themating component, for example, the controller cable 72.

While the present disclosure has been described in detail in connectionwith only a limited number of embodiments, it should be readilyunderstood that the present disclosure is not limited to such disclosedembodiments. Rather, the present disclosure can be modified toincorporate any number of variations, alterations, substitutions orequivalent arrangements not heretofore described, but which arecommensurate with the scope of the present disclosure. Additionally,while various embodiments of the present disclosure have been described,it is to be understood that aspects of the present disclosure mayinclude only some of the described embodiments. Accordingly, the presentdisclosure is not to be seen as limited by the foregoing description,but is only limited by the scope of the appended claims.

1. An electromechanical component arrangement for a gas turbine engine,comprising: a mechanical component disposed at a first side of afirewall of a gas turbine engine; an electronic module in communicationwith the mechanical component, the electronic module separated from themechanical component by a firewall, the firewall comprising a first sideand a second side, the second side having a lower operating temperaturethan the first side; and a vibration isolation structure disposed at thesecond side, the electronic module connected thereto and including atleast one vibration isolator secured to the firewall to vibrationallyisolate the electronic module from gas turbine engine vibrations.
 2. Theelectromechanical component arrangement of claim 1, further comprising acover plate installed over the module opening after the electronicmodule is inserted therethrough.
 3. The electromechanical componentarrangement of claim 1, wherein the electronic module is operablyconnected to one or more of an electrical controller or an electricalmotor disposed at the second side of the firewall.
 4. Theelectromechanical component arrangement of claim 3, the vibrationisolation structure further comprising a connection hub to operablyconnect the electronic module to the one or more of the electricalcontroller or the electrical motor.
 5. The electromechanical componentarrangement of claim 1, wherein the vibration isolator is one or more ofa spring, an elastomeric damper, an air cylinder/piston arrangement oran oil filled cylinder/piston arrangement.
 6. The electromechanicalcomponent arrangement of claim 1, wherein the electronic module isconfigured to collect and indefinitely store data from the mechanicalcomponent relating to the service life and/or operation of themechanical component.
 7. The electromechanical component arrangement ofclaim 1, further comprising an electrical motor disposed at the secondside of the firewall and operably connected to the mechanical componentvia a coupling extending through the firewall at a coupling opening,separate and distinct from the module opening.
 8. The electromechanicalcomponent arrangement of claim 7, further comprising an electricalcontroller disposed at the second side and operably connected to theelectronic module and the electrical motor to control the electricalmotor utilizing input from the electronic module.
 9. Theelectromechanical component arrangement of claim 1, wherein theelectronic module is inseparably affixed to the mechanical component toremain connected to the mechanical component for the entire service lifeof the mechanical component.
 10. The electromechanical componentarrangement of claim 1, wherein the first side has an operatingtemperature greater than 160 degrees Fahrenheit.
 11. Theelectromechanical component arrangement of claim 1, wherein the firewallis disposed axially upstream of a high pressure compressor section ofthe gas turbine engine, the first side disposed axially downstream ofthe firewall.
 12. An electromechanical system for a gas turbine enginecomprising: a mechanical component disposed at a first side of afirewall of a gas turbine engine; an electrical motor disposed at asecond side of the firewall, the second side having a lower operatingtemperature than the first side, the electrical motor operably connectedto the mechanical component via a coupling extending through a couplingopening in the firewall and configured to drive the mechanicalcomponent; an electronic module connected to the mechanical component bya module cable, the electronic module inserted through a module openingin the firewall from the first side to a second side; a vibrationisolation structure disposed at the second side, the electronic moduleconnected thereto and including at least one vibration isolator securedto the firewall to vibrationally isolate the electronic module from gasturbine engine vibrations; and a cover plate installed over the moduleopening after the electronic module is inserted therethrough.
 13. Theelectromechanical system of claim 12, wherein the electronic module isoperably connected to an electrical controller disposed at the secondside of the firewall, the electrical controller configured to controlthe electrical motor utilizing input from the electronic module.
 14. Theelectromechanical system of claim 13, the vibration isolation structurefurther comprising a connection hub to operably connect the electronicmodule to the electrical controller.
 15. The electromechanical system ofclaim 12, wherein the vibration isolator is one or more of a spring, anelastomeric damper, an air cylinder/piston arrangement or an oil filledcylinder/piston arrangement.
 16. The electromechanical system of claim12, wherein the electronic module is configured to collect data from themechanical component relating to the service life and/or operation ofthe mechanical component.
 17. The electromechanical system of claim 16,wherein the data is one or more of operating speeds, temperatures,pressures, flow or operational time of the mechanical component.
 18. Theelectromechanical system of claim 12, wherein the mechanical componentis one of an actuator or a pump.
 19. The electromechanical componentarrangement of claim 12, wherein the first side has an operatingtemperature greater than 160 degrees Fahrenheit.
 20. A gas turbineengine comprising: a firewall, the firewall defining a first sideaxially downstream of the firewall and a second side axially upstream ofthe firewall, the second side having a lower operating temperature thanthe first side; and an electromechanical system including: a mechanicalcomponent disposed at the first side; an electrical motor disposed atthe second side, the electrical motor operably connected to themechanical component via a coupling extending through a coupling openingin the firewall and configured to drive the mechanical component; anelectronic module connected to the mechanical component by a modulecable, the electronic module inserted through a module opening in thefirewall from the first side to a second side; a vibration isolationstructure disposed at the second side, the electronic module connectedthereto and including at least one vibration isolator secured to thefirewall to vibrationally isolate the electronic module from gas turbineengine vibrations; and a cover plate installed over the module openingafter the electronic module is inserted therethrough.